Zero lift split

III.3.1

Zero lift split C601 (factors from HFP-R-311-PF2964)

iM S
gross
covered area lamda 100CF X <J>* 100CM*S 100CD T/C [%] <25
[M2] [M2] [M2] [M2] [%] [°]
Wing I 14.6 516 22 494 0.211 1.46 0.95 144 39.4% 12 30°
Wing II 9.7 608 28 580 0.202 1.37 0.955 152 9.5 31°
Wing III 5.6 179 179 0.261 1.38 0.945 61 9.7 32°
Fuselage 79.8 1640 76 1564 0.167 1.067 279 30.8% _
Horiz.st . 6.9 384 53 331 0.235 1.380 0.93 100 11.0% 10 35°
Vert . st . 9.5 243 243 0.225 1.395 0.90 68 7.5% 11 40°
Engine pod 5.1 232 232 0.230 1.08 58
Pylons 9.6 40 40 0.225 1.37 12 11
Flaps Casing 100CD*S=S (C601) /S (A310) *100CD*S (310) 34
Sum 3739 907 1.198
Interf erence 5.6%
parasi tic 0.67
Sum 1.26

 

The effect of the Reynolds number is shown in the following table.

 

V/T|   [106   1/mJ 5.42 7.22 8.12
Fuselage                 Re
[10 ] 100*Cf
4.28
0.1686
5.7
0.1686
6.41
0.166
Middle  wing         Re
[107] 100*Cf
5.09
0.234
6.79
0.225
7.64
0.221
Average behavior of Cf 1.039 1 0.9805

 

A330 C601
Surface area [m ]
Wing area    [m ]
<P             [°]
1938
362
29
3739
757.15
32
k k orm 1.257
1.055
1.235
1.026

An UHCA was born